Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NN7 MK20 (nn7mk20-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NN7 MK20 (nn7mk20-il)
Reynolds number: 50,000
Max Cl/Cd: 17.25 at α=12°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nn7mk20-il-50000-n5.txt
Download as CSV file: xf-nn7mk20-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NN7 MK20                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3582   0.10960   0.10273  -0.0651   1.0000   0.0484
 -11.750  -0.3649   0.10493   0.09815  -0.0663   1.0000   0.0480
 -11.500  -0.3770   0.09943   0.09275  -0.0681   1.0000   0.0477
 -11.250  -0.3922   0.09451   0.08793  -0.0694   1.0000   0.0472
 -11.000  -0.4153   0.08973   0.08325  -0.0703   1.0000   0.0467
 -10.750  -0.4434   0.08616   0.07978  -0.0696   1.0000   0.0463
 -10.500  -0.4751   0.08347   0.07717  -0.0678   1.0000   0.0459
 -10.250  -0.4981   0.07848   0.07211  -0.0707   0.9943   0.0454
 -10.000  -0.5132   0.07243   0.06585  -0.0765   0.9830   0.0451
  -9.750  -0.5276   0.06763   0.06081  -0.0805   0.9706   0.0449
  -9.500  -0.5385   0.06360   0.05649  -0.0831   0.9581   0.0449
  -9.250  -0.5416   0.05967   0.05220  -0.0848   0.9471   0.0451
  -9.000  -0.5356   0.05584   0.04793  -0.0867   0.9392   0.0458
  -8.750  -0.5310   0.05280   0.04445  -0.0869   0.9299   0.0471
  -8.500  -0.5182   0.04979   0.04083  -0.0877   0.9228   0.0489
  -8.250  -0.5014   0.04738   0.03829  -0.0879   0.9158   0.0510
  -8.000  -0.4734   0.04504   0.03572  -0.0894   0.9116   0.0535
  -7.750  -0.4555   0.04337   0.03380  -0.0886   0.9044   0.0564
  -7.500  -0.4278   0.04158   0.03156  -0.0890   0.8993   0.0609
  -7.250  -0.3909   0.03990   0.02989  -0.0902   0.8964   0.0656
  -7.000  -0.3697   0.03904   0.02884  -0.0888   0.8898   0.0715
  -6.750  -0.3412   0.03805   0.02784  -0.0883   0.8850   0.0781
  -6.500  -0.3097   0.03711   0.02669  -0.0884   0.8813   0.0868
  -6.250  -0.3018   0.03644   0.02613  -0.0858   0.8732   0.0944
  -6.000  -0.2831   0.03547   0.02510  -0.0850   0.8678   0.1050
  -5.750  -0.2742   0.03457   0.02425  -0.0831   0.8609   0.1193
  -5.500  -0.2659   0.03339   0.02324  -0.0816   0.8540   0.1420
  -5.250  -0.2575   0.03158   0.02202  -0.0809   0.8483   0.2031
  -5.000  -0.2599   0.03042   0.02198  -0.0774   0.8404   0.3465
  -4.750  -0.2359   0.03249   0.02466  -0.0720   0.8365   0.4974
  -4.500  -0.2242   0.03351   0.02545  -0.0692   0.8293   0.5541
  -4.000  -0.1762   0.03679   0.02828  -0.0631   0.8204   0.6272
  -3.750  -0.1705   0.03766   0.02904  -0.0585   0.8126   0.6436
  -3.500  -0.1475   0.03812   0.02926  -0.0567   0.8080   0.6598
  -3.250  -0.1182   0.03807   0.02894  -0.0569   0.8048   0.6731
  -3.000  -0.1162   0.03837   0.02915  -0.0529   0.7963   0.6820
  -2.750  -0.0912   0.03830   0.02887  -0.0525   0.7920   0.6927
  -2.500  -0.0689   0.03818   0.02853  -0.0522   0.7876   0.7036
  -2.250  -0.0627   0.03832   0.02858  -0.0490   0.7798   0.7109
  -2.000  -0.0343   0.03807   0.02812  -0.0498   0.7759   0.7193
  -1.750  -0.0235   0.03815   0.02810  -0.0476   0.7694   0.7259
  -1.500  -0.0057   0.03810   0.02788  -0.0471   0.7633   0.7333
  -1.250   0.0250   0.03789   0.02751  -0.0477   0.7599   0.7389
  -1.000   0.0300   0.03815   0.02768  -0.0456   0.7518   0.7462
  -0.750   0.0535   0.03807   0.02748  -0.0451   0.7470   0.7512
  -0.500   0.0868   0.03787   0.02713  -0.0464   0.7440   0.7571
  -0.250   0.0874   0.03834   0.02756  -0.0436   0.7348   0.7629
   0.000   0.1153   0.03825   0.02735  -0.0439   0.7307   0.7680
   0.500   0.1489   0.03873   0.02768  -0.0424   0.7180   0.7785
   0.750   0.1803   0.03862   0.02748  -0.0433   0.7145   0.7830
   1.000   0.1883   0.03926   0.02807  -0.0419   0.7061   0.7881
   1.250   0.2147   0.03934   0.02809  -0.0423   0.7014   0.7921
   1.500   0.2487   0.03921   0.02788  -0.0435   0.6984   0.7958
   1.750   0.2521   0.04015   0.02881  -0.0416   0.6888   0.8003
   2.000   0.2845   0.04022   0.02881  -0.0430   0.6850   0.8040
   2.250   0.2946   0.04095   0.02955  -0.0416   0.6770   0.8075
   2.500   0.3195   0.04123   0.02980  -0.0419   0.6718   0.8112
   2.750   0.3536   0.04122   0.02976  -0.0433   0.6687   0.8147
   3.000   0.3596   0.04242   0.03097  -0.0421   0.6590   0.8185
   3.250   0.3894   0.04250   0.03105  -0.0428   0.6550   0.8217
   3.500   0.3995   0.04352   0.03210  -0.0418   0.6468   0.8253
   3.750   0.4258   0.04388   0.03247  -0.0424   0.6415   0.8291
   4.000   0.4608   0.04391   0.03251  -0.0438   0.6385   0.8325
   4.250   0.4635   0.04535   0.03399  -0.0423   0.6282   0.8360
   4.500   0.4954   0.04543   0.03412  -0.0432   0.6245   0.8395
   4.750   0.5017   0.04686   0.03560  -0.0422   0.6149   0.8437
   5.250   0.5413   0.04838   0.03723  -0.0423   0.6018   0.8514
   5.500   0.5678   0.04876   0.03771  -0.0427   0.5963   0.8553
   6.000   0.6056   0.05046   0.03957  -0.0427   0.5820   0.8641
   6.250   0.6414   0.05019   0.03944  -0.0436   0.5786   0.8690
   6.500   0.6444   0.05199   0.04133  -0.0426   0.5671   0.8744
   6.750   0.6817   0.05159   0.04107  -0.0435   0.5637   0.8797
   7.250   0.6985   0.05459   0.04435  -0.0424   0.5422   0.8927
   7.500   0.7297   0.05452   0.04446  -0.0429   0.5361   0.9016
   7.750   0.7411   0.05598   0.04609  -0.0429   0.5250   0.9142
   8.000   0.7770   0.05519   0.04551  -0.0435   0.5200   0.9820
   8.250   0.7834   0.05701   0.04743  -0.0431   0.5079   1.0000
   8.750   0.8317   0.05800   0.04867  -0.0437   0.4913   1.0000
   9.000   0.8417   0.05964   0.05043  -0.0435   0.4791   1.0000
   9.250   0.8828   0.05836   0.04934  -0.0439   0.4747   1.0000
   9.500   0.8918   0.06003   0.05113  -0.0436   0.4617   1.0000
   9.750   0.9023   0.06155   0.05278  -0.0433   0.4491   1.0000
  10.250   0.9570   0.06078   0.05237  -0.0427   0.4312   1.0000
  10.500   0.9690   0.06194   0.05367  -0.0422   0.4177   1.0000
  10.750   0.9837   0.06271   0.05458  -0.0416   0.4042   1.0000
  11.000   1.0022   0.06289   0.05491  -0.0409   0.3903   1.0000
  11.250   1.0224   0.06274   0.05490  -0.0401   0.3756   1.0000
  11.500   1.0430   0.06246   0.05478  -0.0392   0.3597   1.0000
  12.000   1.0796   0.06259   0.05508  -0.0374   0.3245   1.0000
  12.250   1.0881   0.06406   0.05662  -0.0368   0.3052   1.0000
  12.500   1.1046   0.06444   0.05699  -0.0359   0.2849   1.0000
  12.750   1.1157   0.06560   0.05815  -0.0352   0.2648   1.0000
  13.000   1.1220   0.06747   0.05999  -0.0346   0.2448   1.0000
  13.250   1.1286   0.06930   0.06171  -0.0340   0.2259   1.0000
  13.500   1.1329   0.07158   0.06390  -0.0336   0.2089   1.0000
  13.750   1.1347   0.07434   0.06664  -0.0335   0.1931   1.0000
  14.000   1.1370   0.07711   0.06938  -0.0334   0.1790   1.0000
  14.250   1.1404   0.07977   0.07200  -0.0333   0.1665   1.0000
  14.500   1.1425   0.08282   0.07513  -0.0335   0.1552   1.0000
  14.750   1.1447   0.08592   0.07830  -0.0338   0.1452   1.0000
  15.000   1.1491   0.08864   0.08105  -0.0339   0.1364   1.0000
  15.250   1.1527   0.09161   0.08412  -0.0342   0.1282   1.0000
  15.500   1.1558   0.09477   0.08739  -0.0346   0.1211   1.0000
  15.750   1.1599   0.09760   0.09024  -0.0350   0.1138   1.0000
  16.000   1.1581   0.10163   0.09446  -0.0360   0.1075   1.0000
  16.250   1.1611   0.10470   0.09758  -0.0367   0.1011   1.0000
  16.500   1.1559   0.10932   0.10237  -0.0382   0.0953   1.0000
  16.750   1.1518   0.11360   0.10675  -0.0399   0.0892   1.0000
  17.000   1.1464   0.11824   0.11147  -0.0418   0.0837   1.0000
  17.250   1.1355   0.12414   0.11758  -0.0446   0.0787   1.0000
  17.500   1.1356   0.12760   0.12096  -0.0463   0.0728   1.0000
  17.750   1.1191   0.13523   0.12891  -0.0503   0.0697   1.0000
  18.000   1.1100   0.14123   0.13504  -0.0536   0.0656   1.0000
  18.250   1.1103   0.14497   0.13872  -0.0556   0.0611   1.0000
  18.500   1.0865   0.15524   0.14929  -0.0617   0.0599   1.0000
  18.750   1.0547   0.16864   0.16286  -0.0697   0.0598   1.0000
<< Back to NN7 MK20 (nn7mk20-il)

Polar data table (+)

Polar graphs


<< Back to NN7 MK20 (nn7mk20-il)